FR2866387B1 - Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante - Google Patents

Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante

Info

Publication number
FR2866387B1
FR2866387B1 FR0401384A FR0401384A FR2866387B1 FR 2866387 B1 FR2866387 B1 FR 2866387B1 FR 0401384 A FR0401384 A FR 0401384A FR 0401384 A FR0401384 A FR 0401384A FR 2866387 B1 FR2866387 B1 FR 2866387B1
Authority
FR
France
Prior art keywords
turboreactor
back blow
double blower
aerodynamic adaptation
aerodynamic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
FR0401384A
Other languages
English (en)
French (fr)
Other versions
FR2866387A1 (fr
Inventor
Jacques Bart
Fabienne Lacorre
Yann Lebret
Rousseau Vanessa Le
Patrick Morel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Priority to FR0401384A priority Critical patent/FR2866387B1/fr
Priority to EP05290180A priority patent/EP1566522B1/fr
Priority to DE602005010923T priority patent/DE602005010923D1/de
Priority to ES05290180T priority patent/ES2317168T3/es
Priority to US11/045,365 priority patent/US7299621B2/en
Priority to CA2495992A priority patent/CA2495992C/fr
Priority to JP2005026018A priority patent/JP4237712B2/ja
Priority to UAA200501217A priority patent/UA83995C2/ru
Priority to RU2005103706/06A priority patent/RU2364740C2/ru
Priority to CN2005100091798A priority patent/CN1654804B/zh
Publication of FR2866387A1 publication Critical patent/FR2866387A1/fr
Application granted granted Critical
Publication of FR2866387B1 publication Critical patent/FR2866387B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
FR0401384A 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante Expired - Fee Related FR2866387B1 (fr)

Priority Applications (10)

Application Number Priority Date Filing Date Title
FR0401384A FR2866387B1 (fr) 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
EP05290180A EP1566522B1 (fr) 2004-02-12 2005-01-27 Turboréacteur à double soufflante ayant des aubes directrices à calage variable
DE602005010923T DE602005010923D1 (de) 2004-02-12 2005-01-27 Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln
ES05290180T ES2317168T3 (es) 2004-02-12 2005-01-27 Turborrector con doble soplante que tiene los alabes directores de calado variable.
US11/045,365 US7299621B2 (en) 2004-02-12 2005-01-31 Three-spool by-pass turbojet with a high by-pass ratio
JP2005026018A JP4237712B2 (ja) 2004-02-12 2005-02-02 高いバイパス比を有するスリースプールバイパスターボジェット
CA2495992A CA2495992C (fr) 2004-02-12 2005-02-02 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
UAA200501217A UA83995C2 (ru) 2004-02-12 2005-02-10 Трехкаскадный двухконтурный турбореактивный двигатель с высокой ступенью двухконтурности
RU2005103706/06A RU2364740C2 (ru) 2004-02-12 2005-02-11 Трехкаскадный двухконтурный турбореактивный двигатель с высокой степенью двухконтурности
CN2005100091798A CN1654804B (zh) 2004-02-12 2005-02-16 具有高旁路比的三轴旁路涡轮喷气发动机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0401384A FR2866387B1 (fr) 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante

Publications (2)

Publication Number Publication Date
FR2866387A1 FR2866387A1 (fr) 2005-08-19
FR2866387B1 true FR2866387B1 (fr) 2008-03-14

Family

ID=34707994

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0401384A Expired - Fee Related FR2866387B1 (fr) 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante

Country Status (10)

Country Link
US (1) US7299621B2 (ja)
EP (1) EP1566522B1 (ja)
JP (1) JP4237712B2 (ja)
CN (1) CN1654804B (ja)
CA (1) CA2495992C (ja)
DE (1) DE602005010923D1 (ja)
ES (1) ES2317168T3 (ja)
FR (1) FR2866387B1 (ja)
RU (1) RU2364740C2 (ja)
UA (1) UA83995C2 (ja)

Families Citing this family (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0314123D0 (en) * 2003-06-18 2003-07-23 Rolls Royce Plc A gas turbine engine
DE102004042739A1 (de) * 2004-09-03 2006-03-09 Mtu Aero Engines Gmbh Fan für ein Flugtriebwerk sowie Flugtriebwerk
US7882694B2 (en) * 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
FR2889863B1 (fr) * 2005-08-22 2007-11-02 Snecma Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
US7490461B2 (en) * 2005-10-19 2009-02-17 General Electric Company Gas turbine engine assembly and methods of assembling same
US7685808B2 (en) * 2005-10-19 2010-03-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US7841165B2 (en) * 2006-10-31 2010-11-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US8161728B2 (en) * 2007-06-28 2012-04-24 United Technologies Corp. Gas turbines with multiple gas flow paths
US9359960B2 (en) * 2007-06-28 2016-06-07 United Technologies Corporation Gas turbines with multiple gas flow paths
US8104265B2 (en) * 2007-06-28 2012-01-31 United Technologies Corporation Gas turbines with multiple gas flow paths
US20120222398A1 (en) * 2007-07-27 2012-09-06 Smith Peter G Gas turbine engine with geared architecture
FR2921973B1 (fr) * 2007-10-04 2011-04-29 Snecma Carter intermediaire de turboreacteur et turboreacteur
EP2123884B1 (en) * 2008-05-13 2015-03-04 Rolls-Royce Corporation Dual clutch arrangement
US8128021B2 (en) 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8887485B2 (en) * 2008-10-20 2014-11-18 Rolls-Royce North American Technologies, Inc. Three spool gas turbine engine having a clutch and compressor bypass
FR2942273B1 (fr) * 2009-02-18 2011-06-10 Snecma Moteur double flux a roues de turbine contrarotatives
GB0910955D0 (en) 2009-06-25 2009-08-05 Rolls Royce Plc Adjustable camber aerofoil
US8176725B2 (en) * 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
FR2977635B1 (fr) * 2011-07-04 2017-03-24 Snecma Dispositif d'arbre d'entrainement d'une turbomachine
US9506402B2 (en) 2011-07-29 2016-11-29 United Technologies Corporation Three spool engine bearing configuration
SG11201402663XA (en) * 2012-01-09 2014-09-26 United Technologies Corp Gas turbine engine with geared architecture
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US10036351B2 (en) 2012-04-02 2018-07-31 United Technologies Corporation Geared turbofan with three co-rotating turbines
US10018119B2 (en) * 2012-04-02 2018-07-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
US9074485B2 (en) 2012-04-25 2015-07-07 United Technologies Corporation Geared turbofan with three turbines all counter-rotating
US10036350B2 (en) 2012-04-30 2018-07-31 United Technologies Corporation Geared turbofan with three turbines all co-rotating
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
FR2994452B1 (fr) * 2012-08-09 2016-12-23 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
CN103867337B (zh) * 2012-12-11 2016-02-03 中航商用航空发动机有限责任公司 大涵道比变循环发动机
WO2014133645A2 (en) * 2013-02-20 2014-09-04 Rolls-Royce North American Technologies Inc. Gas turbine engine having configurable bypass passage
FR3003303B1 (fr) * 2013-03-15 2017-06-30 Snecma Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
EP3004595B1 (en) * 2013-06-03 2020-09-02 United Technologies Corporation Turbofan engine bearing and gearbox arrangement
US9777642B2 (en) * 2014-11-21 2017-10-03 General Electric Company Gas turbine engine and method of assembling the same
US10077660B2 (en) 2014-12-03 2018-09-18 General Electric Company Turbine engine assembly and method of manufacturing
CN104500269B (zh) * 2014-12-11 2016-04-20 南京航空航天大学 带内环空气涡轮的自驱动风扇大涵道比涡扇发动机
US10669946B2 (en) 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
FR3039227B1 (fr) * 2015-07-22 2019-12-27 Safran Aircraft Engines Aeronef comprenant un propulseur arriere carene avec stator d’entree a volets mobiles
US20170058831A1 (en) * 2015-08-27 2017-03-02 William Barry Bryan Gas turbine engine having radially-split inlet guide vanes
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
FR3043714B1 (fr) * 2015-11-16 2017-12-22 Snecma Partie avant de turbomachine d'aeronef comprenant une soufflante unique entrainee par un reducteur, ainsi que des aubes directrices de sortie structurales agencees en partie en amont d'un bec de separation
US10563593B2 (en) * 2016-01-04 2020-02-18 Rolls-Royce North American Technologies, Inc. System and method of transferring power in a gas turbine engine
US20170218842A1 (en) * 2016-02-02 2017-08-03 General Electric Company Adjusting Airflow Distortion in Gas Turbine Engine
US10794281B2 (en) 2016-02-02 2020-10-06 General Electric Company Gas turbine engine having instrumented airflow path components
US10753278B2 (en) 2016-03-30 2020-08-25 General Electric Company Translating inlet for adjusting airflow distortion in gas turbine engine
US11073090B2 (en) 2016-03-30 2021-07-27 General Electric Company Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine
BE1025299B9 (fr) * 2017-06-09 2020-05-04 Safran Aero Boosters Sa Compresseur a geometrie variable de turbomachine axiale
US10961921B2 (en) 2018-09-19 2021-03-30 Pratt & Whitney Canada Corp. Model-based control system and method for a turboprop engine
FR3118094A1 (fr) * 2020-12-23 2022-06-24 Safran Aube de stator avec portion mobile, module de turbomachine equipe d’une telle aube de stator et turbomachine correspondante

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1305302A (ja) * 1970-04-28 1973-01-31
US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
GB2155110A (en) * 1984-03-02 1985-09-18 Gen Electric High bypass ratio counter-rotating turbofan engine
GB2194292A (en) * 1986-08-29 1988-03-02 Gen Electric High bypass ratio counterrotating turbofan engine
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
GB8630754D0 (en) * 1986-12-23 1987-02-04 Rolls Royce Plc Turbofan gas turbine engine
US5160251A (en) * 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5388964A (en) * 1993-09-14 1995-02-14 General Electric Company Hybrid rotor blade
US5806303A (en) * 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
US6732502B2 (en) * 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor

Also Published As

Publication number Publication date
RU2364740C2 (ru) 2009-08-20
EP1566522B1 (fr) 2008-11-12
CN1654804B (zh) 2011-06-01
FR2866387A1 (fr) 2005-08-19
EP1566522A1 (fr) 2005-08-24
UA83995C2 (ru) 2008-09-10
RU2005103706A (ru) 2006-07-20
US7299621B2 (en) 2007-11-27
JP4237712B2 (ja) 2009-03-11
CA2495992A1 (fr) 2005-08-12
DE602005010923D1 (de) 2008-12-24
CN1654804A (zh) 2005-08-17
ES2317168T3 (es) 2009-04-16
US20050241291A1 (en) 2005-11-03
JP2005226644A (ja) 2005-08-25
CA2495992C (fr) 2011-11-22

Similar Documents

Publication Publication Date Title
FR2866387B1 (fr) Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
FR18C1024I2 (fr) Derives d'heterocyclocarboxamide
ITTO20050757A1 (it) Compressore d'aria
DE60323595D1 (de) Luftreiniger
DE60333433D1 (de) Luftreinigungsvorrichtung
FR2889565B1 (fr) Compresseur a prelevement d'air centripete
DE602005015466D1 (de) Antivirale 4'-azidonucleoside
MA27248A1 (fr) Navire a coussin d'air
ITTO20030195A1 (it) Condizionatore d'aria.
FR2837877B1 (fr) Modele de superstatoreacteur
DE50209394D1 (de) Klimagebläse
FR2895470B1 (fr) Palier a roulement a passage d'air optionnel
ITTO20030004A1 (it) Condizionatore d'aria
FR2884180B1 (fr) Deflecteur d'air
FR2887259B1 (fr) CONSTRUCTION D'ADNc D'ALPHAVIRUS DE SALMONIDES
ITMI20020496A0 (it) Portone sezionale a tenuta d'aria
FR2845948B1 (fr) Diffuseur d'air.
NO20034051D0 (no) Ventilator
ITMI20030540A1 (it) Compressore d'aria con possibilita' di trasporto perfezionata
FR2852042B1 (fr) Piece d'aretier
ITVC20050001A1 (it) Rasentatore d'aria
DE502004008803D1 (de) Luftdüse
ITMI20021453A1 (it) Condizionatore d'aria
ITSA20020009V0 (it) Separatore aria - liquidi.
UA7437S (uk) Аероіонізатор повітря

Legal Events

Date Code Title Description
CD Change of name or company name
ST Notification of lapse

Effective date: 20101029